EP2775202B1 - Luftwirbler - Google Patents

Luftwirbler Download PDF

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Publication number
EP2775202B1
EP2775202B1 EP14157662.9A EP14157662A EP2775202B1 EP 2775202 B1 EP2775202 B1 EP 2775202B1 EP 14157662 A EP14157662 A EP 14157662A EP 2775202 B1 EP2775202 B1 EP 2775202B1
Authority
EP
European Patent Office
Prior art keywords
swirler
injector
wall
longitudinal axis
swirl
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP14157662.9A
Other languages
English (en)
French (fr)
Other versions
EP2775202A3 (de
EP2775202A2 (de
Inventor
Gary Chew
Viraphand Cholvibul
Philip E. O. Buelow
Jason A. Ryon
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Collins Engine Nozzles Inc
Original Assignee
Delavan Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
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Publication of EP2775202A2 publication Critical patent/EP2775202A2/de
Publication of EP2775202A3 publication Critical patent/EP2775202A3/de
Application granted granted Critical
Publication of EP2775202B1 publication Critical patent/EP2775202B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • F23D11/102—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
    • F23D11/103—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber with means creating a swirl inside the mixing chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • F23D11/105—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet at least one of the fluids being submitted to a swirling motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F23D14/24—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing

Definitions

  • the present invention relates to nozzles and injectors, and more particularly to swirlers for nozzles and injectors in gas turbine engines.
  • compressor discharge air is used to atomize liquid fuel. More particularly, the air provides a mechanism to break up a fuel sheet into a finely dispersed spray that is introduced into the combustion chamber of an engine. Quite often the air is directed through a duct that serves to turn or impart swirl to the air. This swirling air flow acts to stabilize the combustion reaction.
  • Helically vaned swirlers were used because of their ability to effectively turn the air flow. These helical vanes generated acceptable air flow characteristics for many engine applications. Helically vaned air swirlers are traditionally placed upstream in the internal air path of a nozzle. Fuel injected into the swirling flow is mixed with air for combustion downstream.
  • EP 1605204 discloses a conical swirler having a cone-shaped body and vanes cut into the body.
  • US 6360776 discloses an apparatus for mixing fuel with an oxidising agent comprising an inner body that includes slots that extend radially through the inner body.
  • the invention provides an injector according to claim 1 comprising: an injector body with opposed inlet and outlet ends with a liquid flow circuit passing through the injector body from the inlet end to the outlet end, wherein an inner air circuit is defined through the injector body along a longitudinal axis; and a swirler mounted to the injector body having a swirler body with opposed inlet and outlet ends with a swirler wall extending within the inner air circuit and extending between the opposed inlet and outlet ends along a longitudinal axis, the inlet end of the swirler body defining an inlet opening, wherein a plurality of swirl slots is defined through a portion of the swirler wall that converges toward the longitudinal axis in a direction from the inlet opening toward the outlet end of the swirler body, wherein the swirl slots are radially off-set with respect to the longitudinal axis for imparting swirl on a flow passing from the inlet opening, through the swirl slots, and past the outlet end of the swirler body, wherein the only flow path through the swirler wall is through the swirl
  • the swirl slots are elongated in a direction along the swirler wall.
  • Each swirl slot can extend along the swirler wall in a direction oblique axially and circumferentially relative to the longitudinal axis.
  • the swirler wall can define an axial cross-sectional profile that is bullet-shaped.
  • the swirler wall defines an axial cross-sectional profile that is trapezoidal.
  • the outlet end of the swirler body can include a planar portion of the swirler wall that is substantially perpendicular to the longitudinal axis.
  • the swirl slots can be cylindrical bores through the swirler wall.
  • a flow passage is defined between the swirler wall and a wall of the inner air circuit of the injector body.
  • the flow passage can have a cross-sectional area that increases in a direction along the longitudinal axis towards the downstream end of the swirler.
  • the swirl slots can feed into the flow passage.
  • FIG. 1 a partial view of an exemplary embodiment of an injector in accordance with the invention is shown in Fig. 1 and is designated generally by reference character 100.
  • Other embodiments of injectors in accordance with the invention, or aspects thereof, are provided in Figs. 2-5 , as will be described.
  • the systems and methods of the invention can be used to provide a swirling flow, for example in inner air circuits of fuel injectors.
  • injector 100 includes an injector body 102 with opposed inlet and outlet ends 104 and 106, respectively.
  • a liquid flow circuit 108 passes through injector body 102 from inlet end 104 to outlet end 106.
  • An inner air circuit 110 is defined through injector body 102 along longitudinal axis A.
  • a swirler 112 is mounted to injector body 102.
  • swirler 112 includes a swirler wall 114 extending within inner air circuit 110, as shown in Fig. 1 , from an upstream inlet end of swirler 112 to an opposed downstream outlet end 118 of swirler 112 along longitudinal axis A.
  • the inlet end of swirler 112 defines an inlet opening 116 where air can be introduced to the interior space within swirler wall 114.
  • a plurality of swirl slots 120 is defined through swirler wall 114.
  • Swirl slots 120 are radially off-set with respect to longitudinal axis A.
  • One of the swirl slots 120 is circled to indicate the swirl slot defined directly into and out of the viewing plane as viewed in Fig. 2 , which is below longitudinal Axis A. Since all of the swirl slots 120 are radially off-set in this manner, they impart swirl on a flow passing from the inlet opening 116, through swirl slots 120, and past downstream end 118 of the swirler body.
  • swirl slots 120 are defined through a portion of the swirler wall 114 that converges toward longitudinal axis A in a direction from the inlet opening 116 toward outlet end 118 of the swirler body.
  • Swirl slots 120 are elongated in a direction along swirler wall 114.
  • Each swirl slot 120 extends along swirler wall 114 in a direction oblique axially and circumferentially relative to longitudinal axis A. In other words, each slot 120 extends partly circumferentially around swirler wall 114 it extends along swirler wall 114 in the axial direction.
  • swirler wall 114 defines an axial cross-sectional profile that is bullet-shaped. As also shown in Fig. 3 , the downstream outlet end 118 of swirler wall 114 is closed off so the only flow path through swirler wall 114 is through swirl slots 120.
  • a flow passage 122 is defined between swirler wall 114 and the wall of inner air circuit 110 of injector body 102.
  • Flow passage 122 has a cross-sectional area that increases in the direction along longitudinal axis A towards the downstream outlet end 118 of swirler 112. Swirl slots 120 feed into flow passage 122. This arrangement of swirl slots 120 and flow passage 122 causes high velocity air flow to be closer to the fuel injection point of liquid flow circuit 108 than would be the case for traditional swirlers. This can enhance atomization of the liquid issued from circuit 108, for example enhancing fuel atomization in fuel injection applications.
  • swirl slots 120 and 220 described above are elongated slots
  • cylindrical slots can also be used.
  • injector 300 includes an injector body 302 and swirler 312 much as those described above except that swirl slots 320 are radially off-set cylindrical bores through the swirler wall.
  • This discrete jet type configuration creates a swirling flow pattern that is suitable for certain applications.
  • the swirl slots described herein can all be formed by any suitable process, such as milling or any other suitable process.
  • the milling plane for one swirl slot 120 indicated with the dashed line around the swirl slot 120 in Fig. 1 is parallel with the viewing plane.
  • Each of the swirlers described herein can be formed as a single piece mounted to the respective injector body by brazing or any other suitable process.
  • injectors 100, 200, and 300 described above include swirlers having bullet-shaped cross-sectional profiles, any other suitable cross-sectional profile can be used as well.
  • injector 400 in Fig. 5 includes a swirler 412 having a swirler wall with a trapezoidal cross-sectional profile.
  • the outlet end 418 of this swirler body includes a planar portion of the swirler wall that is substantially perpendicular to longitudinal axis A.
  • swirlers as described herein over traditional axial type swirlers, which typically include a centerline bluff body, is related to thermally induced stresses. Swirlers as described herein can tend to undergo relatively uniform temperature changes compared to traditional swirlers with bluff bodies. The bluff bodies tend to have large thermal masses, resulting in considerable thermal gradients across the swirl vanes, which is not necessarily the case with swirlers as described herein.
  • injectors and swirlers as described herein can be used in any other suitable application.
  • injectors and swirlers as described herein can be used to swirl any suitable fluid, including liquids, as needed for specific applications.
  • Various embodiments are described herein with features that vary from embodiment to embodiment to provide different flow characteristics. Those skilled in the art will readily appreciate that any of these features can be adapted and/or used in combination to suit specific applications.
  • swirlers described herein are shown mounted in exemplary injector bodies, those skilled in the art will readily appreciate that swirlers as described herein can be used in any other suitable type of injector, nozzle, or other envelope without departing from the scope of the invention. In short, the swirlers described herein provide considerable design flexibility so that the flow characteristics can be tailored for specific applications.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (5)

  1. Einspritzdüse (100; 300; 400), umfassend:
    einen Einspritzdüsenkörper (102; 302) mit einander gegenüberliegendem Einlassende (104) und Auslassende (106) mit einem Flüssigkeitströmungskreislauf (108), der durch den Einspritzdüsenkörper vom Einlassende zum Auslassende strömt, wobei ein innerer Luftkreislauf (110) durch den Einspritzdüsenkörper entlang einer Längsachse (A) definiert ist; und
    einen am Einspritzdüsenkörper angebrachten Wirbler (112; 312; 412), der einen Wirblerkörper mit einander gegenüberliegendem Einlassende und Auslassende (118) aufweist, wobei sich eine Wirblerwand (114) innerhalb des inneren Luftkreislaufs erstreckt und sich zwischen dem sich gegenüberliegenden Einlassende und Auslassende (118) entlang einer Längsachse (A) erstreckt, wobei das Einlassende des Wirblerkörpers eine Einlassöffnung (116) definiert, wobei eine Vielzahl von Wirbelschlitzen (120; 320) durch einen Abschnitt der Wirblerwand, der in Richtung der Längsachse in einer Richtung von der Einlassöffnung zum Auslassende des Wirblerkörpers konvergiert, definiert ist, wobei der einzige Strömungspfad durch die Wirblerwand durch die Wirbelschlitze verläuft,
    und wobei die Wirbelschlitze in Bezug auf die Längsachse radial versetzt sind, um einer Strömung, die von der Einlassöffnung durch die Wirbelschlitze und aus dem Auslassende des Wirblerkörpers strömt, einen Wirbel zu verleihen.
  2. Einspritzdüse nach Anspruch 1, wobei die Wirbelschlitze (120) in einer Richtung entlang der Wirblerwand länglich sind, wobei sich vorzugsweise jeder Wirbelschlitz entlang der Wirblerwand in einer Richtung axial schräg und in Umfangsrichtung relativ zu der Längsachse erstreckt.
  3. Einspritzdüse nach Anspruch 1 oder 2, wobei die Wirblerwand ein axiales Querschnittsprofil definiert, das kugelförmig ist oder
    wobei die Wirblerwand ein axiales Querschnittsprofil definiert, das trapezförmig ist und wobei das Auslassende des Wirblerkörpers einen ebenen Abschnitt der Wirblerwand beinhaltet, der im Wesentlichen senkrecht zur Längsachse ist.
  4. Einspritzdüse nach Anspruch 1 oder 3, wobei die Wirbelschlitze (320) zylindrische Bohrungen durch die Wirblerwand sind.
  5. Einspritzdüse nach einem beliebigen vorstehenden Anspruch,
    wobei ein Strömungskanal (122) zwischen der Wirblerwand und einer Wand des inneren Luftkreislaufs des Einspritzdüsenkörpers definiert ist, wobei der Strömungskanal einen Querschnittsbereich aufweist, der sich in einer Richtung entlang der Längsachse zum stromabwärtigen Ende des Wirblers vergrößert, wobei vorzugsweise die Wirbelschlitze in den Strömungskanal führen.
EP14157662.9A 2013-03-04 2014-03-04 Luftwirbler Active EP2775202B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/783,832 US10161633B2 (en) 2013-03-04 2013-03-04 Air swirlers

Publications (3)

Publication Number Publication Date
EP2775202A2 EP2775202A2 (de) 2014-09-10
EP2775202A3 EP2775202A3 (de) 2015-01-07
EP2775202B1 true EP2775202B1 (de) 2017-10-18

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EP (1) EP2775202B1 (de)

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US9939155B2 (en) * 2015-01-26 2018-04-10 Delavan Inc. Flexible swirlers
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CN109642724A (zh) * 2016-07-26 2019-04-16 杰富意钢铁株式会社 电炉用助燃燃烧器
US11131459B2 (en) 2017-09-26 2021-09-28 Delavan Inc. Combustor with an air mixer and an air swirler each having slots
US10788214B2 (en) * 2018-04-10 2020-09-29 Delavan Inc. Fuel injectors for turbomachines having inner air swirling
US11143406B2 (en) * 2018-04-10 2021-10-12 Delavan Inc. Fuel injectors having air sealing structures
CN109059534B (zh) * 2018-06-12 2024-02-23 湖北锋焰机电科技有限公司 一种可调节式高效节能回转窑燃烧器
US10935245B2 (en) * 2018-11-20 2021-03-02 General Electric Company Annular concentric fuel nozzle assembly with annular depression and radial inlet ports
CN109915826A (zh) * 2019-03-19 2019-06-21 苏州墨华高科信息技术有限公司 一种自转旋流槽与旋流室相结合的喷嘴
CN111706878A (zh) * 2020-06-01 2020-09-25 滁州帝邦科技有限公司 双油路对冲直射式喷嘴
JP2024101934A (ja) * 2023-01-18 2024-07-30 トヨタ自動車株式会社 水素ガスタービンに適した燃焼器及びその燃焼ノズル

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US10161633B2 (en) 2018-12-25
EP2775202A3 (de) 2015-01-07
US20190101291A1 (en) 2019-04-04
US20140245742A1 (en) 2014-09-04
EP2775202A2 (de) 2014-09-10

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